Turbine-engine.



S. Z. DE FERRANTI.

TURBINE ENGINE. APPLIOATION FILED NOV. 12, 1904.

1,045,% 1 Patented Dec. 3, 1912. Y 4 sums-sum 1.

fave/czar JEans-rmrv Z. 06 FERKnA/ S. Z. DE PERRANTI. TURBINE ENGINE. APPLICATION FILED NOV. 12, 1904. 1,045,96 1 Patented D60. 3, 1912.

WM M

8. Z. DE- PERRANTI.

TURBINE ENGINE.

APPLICATION FILED NOV.12, 1904.

4 SHEETS-SHEET 3.

1,045,961. Patented Dec.3, 1912.

S. Z. DE FERRANTI.

TURBINE ENGINE.

APPLIOATION FILED NOV. 12, 1904.

Patented Dec.3,1912.

4 SHEETS-SHEET 4.

FFICE.

l SEBASTIAN ZIANI DE FEBRANTI, OF LONDON, ENGLAND.

TURBINE-ENGINE.

Specification of Letters Patent.

Patented Dec. 3, 1912.

Application filed November 12, 1904. Serial No. 232,525.

To all whom it may concern.-

Be it known thatl, SEBASTIAN ZIANI on FEBRANTI', a subject of the "King of Great Britain and Ireland, residing at 31 Lynd-, hurst road, Hampstead London, N. W., England, have invented certain pew and useful Improvements in or Relatlng to Turbine Engines, of which the fOllOWIDg IS a specification.

' This invention relates to power installations in which a turbine is supplied with air and products of combustion as the working fluid, the constituent elements of this working fluid havin been first necessamly compressed to a big pressure in order to secure a good economy.

It is found that to achieve commercial success in power installations of the type in question, great care has to be taken to reduce the cost and complexity of the compressing plant to a minimum and at the same time to lessen as far as-possible the negative work spent in the compressing 0 eratlon.

Varioup combinations 0 elements to form the complete power installation and various cycles of operations have been proposed heretofore in this art but the present inven- 'tion'differs from all previous attempts masmuch as it includes at the same time the following essential and salient features as component elements of the complete installation,

-viz.: (a) multiple stage compression of the elastic fluid medium in a low cost apparatus with cooling between the stages, so that compression is practically isothermal; (b) imparting of the heat to the fluid at the maximum pressure of the cycle by internal combustion; (0) expansion in a single stage down to a temperature workable in the blades of the turbine and (d) extraction of the velocity due to the expansion in a multiple stage impact turbine.

It will be understood that when describing the compression stage above, I intend the term practically isothermal to include the case of a series of adiabatic compressions with cooling between stages, thus being on the Whole substantially isothermal it may include the case in which the last stage alone of the compression is adiabatic.

Referring to the accompanying drawings which form part of the specification, I- will now describe various arrangements of apparatus for carryingbmy invention into effect.

Figure 1 shows a turbine, the combustion chamber of which is supplied with compressed air from a stage compressor; Fig. 2 shows a similar installation but provided with a compressor using liquid as the medium of compression; 1 1g. 2 shows a similar installation to that shown in Fig. 2, but provided with a rotary blower for the primary and a reciprocating compressor, for the final stage of the compression; Fig. 3 shows a series of turbine driven compressors feeding into a common reservoir from which the turbines doing useful work draw their supplies,

All the drawings are of a diagrammatic nature, individual pipes, for example, being in man instances represented by a single line; w ere desirable, similar parts of the. apparatus 1n the different figures are denoted by the same reference symbols.

In carrying the invention into effect ac- Jrding to one form, the compressor, as one element of the complete power generator, may take any of the different forms mentioned above or a stage turbo-compressor, a, i. 6., a reverse turbine with blades modified to form a compressor (see Fig. 1) with coolers, b, disposed between stages so as to give a substantially isothermal compression may be used with or without the addition of a reciprocating piston compressor for the final stage. The compressed air passes by way of the pipes, 0, through the regenerators, d. and thence through the pipes, e, to the combustion chamber. This part of the apparatus is preferably duplicated, as shown in the figure, though for convenience only one operative set of the different elements will be described. The combustion chamber consists of an outershell, f, and an inner shell, h, from which at one end the nozzle (or nozzles) issues and to which at the other end fuel is supplied through the pipe, 2'. This fuel may be either gas or liquid or solid fuel in a finely divided state. Holes, 70, are also formed in the inner shell at this end to allow the compressed air after passing between the outer and inner shells to enter the latter and supply oxygen for the combustion of the fuel.

The combustion chamber may be water jacketed or lined with refractory material or both or again it may be lined and lagged and is preferably arranged in such relation i prodilcts of combustion down to a low tem- The turbine m, itself, which is shown in the figure as driving its own compressor,

' a, and a dynamo, '11., may consist of impact wheels with such a suitable nuniber of actions as will enable it to deal with the issuing velocity, the whole of the expansion however being carried out' in a single stage in the nozzle. Or a single wheel may be used with the fluid thrownback on it the necessary number of times or a combination of both forms.

The turbine may with advantage be of 5type described in my Patent No. 2565 of The system thus includes a rotary multiple compression stage isothermal compressor together with a single expansion stage turbine. The products of combustion after giving up energy to the turbine pass through the regenerator, d, to the exhaust, 0, thereby raising the temperature of the compressed air on its way to the combustion chamber to as nearly that of the exhaust gases as possible. structurally, the regenerator may be of any convenient tube pattern as indicated or otherwise. Where gas is used as a fuel, a separate compressor. and regenerator of any of the above forms may be used for the gas as distinct from the ,air. It will be seen that in carrying my invention into eflect, the component elements of the complete generator may take other forms-than those described above by way of example without departing from the es sence of the invention.

,According to a modified form of the invention, as shown in Fig. 2, a rotary air compressor of the type in which liquid is used as the medium of compression and energy is imparted to the liquid by a rotary device, is substituted for the stage turbocompressor indicated in Fig. 1. Such an air compressor may be of the type for which a British patent, No. 22846/02 has been granted, or again, it may be of the well known hydraulic type in which a stream of water moving under gravity entrains and compresses air but modified in so far 'as the water is circulated by and receives energy from a rotary device.

' One form of such a suitable compressor V .will be described by wa of example.

A rotary thrower, r, aving for example, two hollow arms and shown as driven by the turbine, m, receives water, through the nozzle, 8. As the thrower rotates at a high speed, the solid jets of water issuing therefrom are caused to pass over the open ends.

ofa series of compressing tubes, t, which in end view are arranged in a com lete circle surrounding the thrower. e mlet ends .of these tubes being as close as possible together and separated only by thin partitions or dividing walls with sharpened edges; the efiect of this high velocity wt of water passing over them is to shoot plugs pressed being entraine between these plugs. The compressing tubes lead into a hollow annular chamber, 1, from which a pipe, '0, passes to the air and water separator chamber, 10. The water separated in this chama ber passes byway of the pipe, :0, to a cooler, z, whence it is returned to the thrower through the contracting nozzle, 8., ipes, 2 and 3, are provided, by means of which cold water is circulated through the cooler, z. The compressed air from the separator, 20, passes through the pipe, 4, which branches into two parts leading respectively to the regenerators, d. In some cases however I may inclose the thrower 1'. (Fig. 2) in a casing, 46, and deliver to the chamber 51 air which has been already compressed in a rotary blower 48, by wa of a cooler, 49, and a pipe 50. The air t en passes to the separator 'w, as above described, from thence to a reciprocatingrcompressor 47,

of water into the tubesi t, the air to be comwhere it receives its final compression after 9 In some cases the turbine which gives out the power for useful work may not itself drive any compressor at all; but in this case it is fed from a reservoir which is supplied by a separately drivencompressor as above. Or again, a plurality of turbines doing useful work may be fed in parallel from a com= mon reservoir which is itself supplied by one or more separately driven compressors.

Thus, referring to Fig. 3, a common compressed air reservoir, 5, is shown fed by, for

example, three multi-stage compressors, 6, each supplied with coolers 7, between stages so as to give a substantially isothermal compresslon; each of these compressors is driven by a turbine, 8, of the type described above,

air being supplied to the combustion chamber, 9, from'the common reservoir, 5, by Way, of the pipe, 10, regenerator, 11, and pipe, 12. This part of the apparatus constitutes the compressor system.

Where as is used as the fuel there is a correspon ing system for the gas to that already described for the air, the combustion chamber being fed from the gas main. Oil can in like manner be stored under pressure, (the pressure if necessary being obtained from the air reservoir,) and forced into the combustion chambers. The motor system, as shown by way of ex- I l I. n. i a ample n the figure comprises three turbines, m, eac driving a dynamo, Each turbine is,as bove, supplied with working fluid tain elements have been described above inrelation to one system of working only, neverthelessl may adapt such elements 1f desirable, to form component parts of other systems described in this specification, wi h out going beyond the limits of the inventi 11.

From the above description it Will be seen that the essential features of my invention are; multiple stage compression of the clastic fluid medium in a low cost apparatus with cooling. between the stages, so that compression is practically isothermal; imparting of the heat to the fluid at the maximum pressure of the cycle by internal combustion; expansion in a single stage down to a temperatur'e workable in the blades of the turbine and extraction of the velocity due to the expansion, in a multiple stage impactturbine.

Again, although I have described the tur; bine as having a regenerator this may be omitted if the compression pressure be raised to such a point that the expansion to the exhaust pressure is sufficient to absorb practically all the heat in the Working fluid so that it dischargeset practically atmospheric pressure.

I claim as new and desire to secure by Letters Patent is:

1-. A power installation comprising incombination a combustion turbine and means for absorbing the power developed thereby; a second combustion turbine and an air compressor driven thereby; an air reservoir into which said compressor delivers, combustion chambers operatively connected to each of said turbines together with means for delivering air from said reservoir to the combustion chambers of each of the above menturbine t rough said regenerator.

Having thus described my invention what 3: A power installation comprising in combination a combustion turbine driving an air, compressor; a second combustion turbine and means for absorbing the power developed thereby; combustion chambers opera: tively connected to said turbines, means for delivering air from saidcompressor to the combustion chamber of said turbine driving it, said means including as part of it a reg'enerator together with means for passing exhaust ases from said compressor-driving 4. A power installation comprising in combination, a combustion turbine driving an air compressor; a second combustion turbine and means for absorbing the power devel- J oped thereby; combustion chambers operatively connected to said turbines, means for delivering air from said compressor to the combustion chamber of one of said turbines, said means including as part of it a regenorator together with means for passing exhaust gases from one of said turbines through said regenerator.

5. A. power installation comprising in combination a combustion turbine driving an air compressor; a second combustion turbine and means for absorbing the power developed thereby; combustion chambers operatively connected to said turbines, means for leading compressed air from said compressor to the combustion chambers of each of said turbines said leading means having parts in duplicate with a regenerator in each of said parts together with means for passing exhaust gases from said turbines through said regenerators;

6. A power installation comprising in combination, a combustion turbine driving an aircompressor; a second combustion turbine and means for absorbing the power developed thereby; combustion chambers operatively connected to said turbines, means for leading compressed air from said compressor to the combustion chambers of each of said turbines said leading means including ducts 7 connected respectively toeeach of said turbinesiand a regenerator in each of said ducts, together with means for passing exhaust gases from each of said turbines through the regenerator disposed in the duct connected thereto 7 A power installation comprising in combination a combustion turbine driving an air compressor; a second combustion turbine mechanically independent of said first mentioned turbine and means for absorbin the power developed thereby, combustion 0 am bers operatively connected to said turbines; together with means for leading air from said compressor to the combustion chambers of each of said turbines said leading means including regenerative means for heating said fluid.

' 8. A power installation comprising in comthereby; combustion chambers operatively bination, a plurality'of combustion turbines bustion chambers of the individual turbines 10 and means for absorbing the power develof. both said pluralities. oped thereby; a second plurality of combus- In witness whereof I have hereunto set tion turbines and air compressors drivenmy hand in presence of two witnesses.

connected to each of said turbines; together SEBASTIAN ZIANI DE FERRANTI' with a common reservoir into which all said Witnesses:

air compressors deliver and connectionsbe- Romm'r MORRISON NmLsoN,

tween said reservoir and each of the "com- WILLIAM CAs'rLE. 

